CN114626146A - Simulation method for combined power system - Google Patents
Simulation method for combined power system Download PDFInfo
- Publication number
- CN114626146A CN114626146A CN202210331010.8A CN202210331010A CN114626146A CN 114626146 A CN114626146 A CN 114626146A CN 202210331010 A CN202210331010 A CN 202210331010A CN 114626146 A CN114626146 A CN 114626146A
- Authority
- CN
- China
- Prior art keywords
- turbine
- channel
- spray pipe
- stamping
- engine
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Granted
Links
- 238000004088 simulation Methods 0.000 title claims abstract description 33
- 238000000034 method Methods 0.000 title claims abstract description 28
- 239000007921 spray Substances 0.000 claims abstract description 34
- 238000012935 Averaging Methods 0.000 claims abstract description 8
- 238000004364 calculation method Methods 0.000 claims description 18
- 238000002485 combustion reaction Methods 0.000 claims description 7
- 230000004907 flux Effects 0.000 claims description 6
- 238000013178 mathematical model Methods 0.000 claims description 6
- 238000006243 chemical reaction Methods 0.000 claims description 4
- 238000012937 correction Methods 0.000 claims description 4
- 238000002940 Newton-Raphson method Methods 0.000 claims description 3
- 239000004744 fabric Substances 0.000 claims description 3
- 238000004590 computer program Methods 0.000 claims 1
- 230000008878 coupling Effects 0.000 abstract description 2
- 238000010168 coupling process Methods 0.000 abstract description 2
- 238000005859 coupling reaction Methods 0.000 abstract description 2
- 230000002457 bidirectional effect Effects 0.000 abstract 1
- 238000011144 upstream manufacturing Methods 0.000 abstract 1
- 230000015654 memory Effects 0.000 description 8
- 230000006870 function Effects 0.000 description 3
- 238000011160 research Methods 0.000 description 3
- 230000035939 shock Effects 0.000 description 3
- 238000013461 design Methods 0.000 description 2
- 230000003287 optical effect Effects 0.000 description 2
- 239000002243 precursor Substances 0.000 description 2
- 230000003068 static effect Effects 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000004422 calculation algorithm Methods 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 230000010354 integration Effects 0.000 description 1
- 238000012545 processing Methods 0.000 description 1
Images
Classifications
-
- G—PHYSICS
- G06—COMPUTING; CALCULATING OR COUNTING
- G06F—ELECTRIC DIGITAL DATA PROCESSING
- G06F30/00—Computer-aided design [CAD]
- G06F30/10—Geometric CAD
- G06F30/15—Vehicle, aircraft or watercraft design
-
- G—PHYSICS
- G06—COMPUTING; CALCULATING OR COUNTING
- G06F—ELECTRIC DIGITAL DATA PROCESSING
- G06F30/00—Computer-aided design [CAD]
- G06F30/20—Design optimisation, verification or simulation
- G06F30/23—Design optimisation, verification or simulation using finite element methods [FEM] or finite difference methods [FDM]
-
- G—PHYSICS
- G06—COMPUTING; CALCULATING OR COUNTING
- G06F—ELECTRIC DIGITAL DATA PROCESSING
- G06F30/00—Computer-aided design [CAD]
- G06F30/20—Design optimisation, verification or simulation
- G06F30/28—Design optimisation, verification or simulation using fluid dynamics, e.g. using Navier-Stokes equations or computational fluid dynamics [CFD]
-
- G—PHYSICS
- G06—COMPUTING; CALCULATING OR COUNTING
- G06F—ELECTRIC DIGITAL DATA PROCESSING
- G06F2111/00—Details relating to CAD techniques
- G06F2111/10—Numerical modelling
-
- G—PHYSICS
- G06—COMPUTING; CALCULATING OR COUNTING
- G06F—ELECTRIC DIGITAL DATA PROCESSING
- G06F2113/00—Details relating to the application field
- G06F2113/08—Fluids
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T90/00—Enabling technologies or technologies with a potential or indirect contribution to GHG emissions mitigation
Landscapes
- Engineering & Computer Science (AREA)
- Physics & Mathematics (AREA)
- Theoretical Computer Science (AREA)
- General Physics & Mathematics (AREA)
- Geometry (AREA)
- Evolutionary Computation (AREA)
- General Engineering & Computer Science (AREA)
- Computer Hardware Design (AREA)
- Mathematical Analysis (AREA)
- Mathematical Optimization (AREA)
- Pure & Applied Mathematics (AREA)
- Fluid Mechanics (AREA)
- Mathematical Physics (AREA)
- Computing Systems (AREA)
- Algebra (AREA)
- Automation & Control Theory (AREA)
- Aviation & Aerospace Engineering (AREA)
- Computational Mathematics (AREA)
- Management, Administration, Business Operations System, And Electronic Commerce (AREA)
Abstract
The invention discloses a simulation method for a combined power system, which comprises the following steps: acquiring air flow parameters entering a turbine channel and a stamping channel; respectively converting the gas flow parameters of the turbine channel and the stamping channel into first one-dimensional data and second one-dimensional data at an interface through area averaging or mass averaging; and inputting the first one-dimensional data and the second one-dimensional data into the corresponding turbine engine and the corresponding ramjet engine, so that the internal and external rheological dimension integrated numerical simulation of the combined power system is performed, the bidirectional coupling simulation of the state change of the combined engine on the flow of an upstream air inlet system and a downstream spray pipe can be realized, and the internal and external flow integrated aerodynamic performance numerical simulation of the aircraft and the combined power engine thereof is realized.
Description
Technical Field
The invention relates to the field of aircrafts, in particular to an internal and external flow integrated simulation method for a combined power system.
Background
The hypersonic aircraft adopts a combined power system to accelerate the aircraft from ground takeoff to hypersonic speed, the adopted propulsion systems are a turbine engine and a ramjet engine, wherein the turbine engine is responsible for accelerating the aircraft from a ground static state to about Ma 2.5, the turbine engine exits from circulation, and meanwhile, the ramjet engine starts to ignite to work and continuously accelerates the aircraft to hypersonic speed. In order to realize the coupling simulation of the integration of the inner flow and the outer flow of the hypersonic aircraft, not only the simulation of an air inlet and exhaust system needs to be completed, but also the combined simulation of the air inlet and exhaust system and a turbine/ramjet combined engine needs to be carried out, and if a turbine/ramjet flow passage is completely calculated, the grid quantity required by numerical simulation cannot be accepted, and the pre-research progress is seriously slowed.
Disclosure of Invention
In order to solve the problems, the invention provides a simulation method for a combined power system, which has small calculation amount and high simulation speed.
In order to achieve the purpose, the invention provides the technical scheme that: a simulation method for a combined power system, comprising:
step one, acquiring air flow parameters entering a turbine channel and a stamping channel;
secondly, converting the air flow parameters of the turbine channel and the stamping channel into first one-dimensional data and second one-dimensional data through area averaging or mass averaging at an interface respectively;
inputting the first one-dimensional data into a turbine engine, and determining the inlet parameters of a turbine channel spray pipe by the turbine engine by adopting a component characteristic model;
fourthly, the turbine channel spray pipe performs flow field characteristic calculation by utilizing the inlet parameters of the turbine channel spray pipe, so that the flow characteristic of the turbine channel spray pipe is obtained;
inputting the second one-dimensional parameters into a ramjet engine, and determining inlet parameters of a spray pipe of a stamping channel by the ramjet engine through a quasi one-dimensional mathematical model;
and sixthly, calculating the flow field characteristic of the stamping channel spray pipe according to the inlet parameter of the stamping channel spray pipe, and obtaining the flow characteristic of the stamping channel spray pipe.
As a preferred technical solution, the second step further comprises:
multiplying the airflow parameter in each grid unit by the area or flow of the grid unit, then summing the parameters of the whole interface, and finally dividing by the area or flow of the interface, thereby obtaining the parameter of area average or quality average;
as a preferred technical solution, the third step further includes:
determining an initial value of a preset parameter of the turbine engine from the first one-dimensional data;
performing iterative updating according to a common working condition equation and by adopting a Newton-Raphson method for the initial values of the preset parameters, and when the error is less than 10-4And when so, stopping iteration.
As a preferred technical scheme, the preset parameters include a compressor rotation speed, a compressor auxiliary coordinate and a turbine pressure drop ratio.
As a preferred technical solution, the step four further includes:
assigning a nozzle inlet parameter to an interface between the turbine engine and the turbine path nozzle;
and the turbine channel spray pipe performs flow field characteristic calculation according to the calculation result of the turbine engine so as to obtain the flow characteristic of the turbine channel spray pipe.
As a preferred technical solution, the fifth step further includes:
a double-module stamping combustion chamber of the stamping engine adopts a quasi-one-dimensional mathematical model for analysis;
calculating to obtain stroke parameters of the ramjet by solving a conservation quasi-one-dimensional control equation;
wherein
In order to solve the vector, the vector is calculated,
in the form of a flux vector, the flux vector,
the following are defined for the source terms:
wherein,
adding terms for mass;
is the wall friction coefficient; equivalent diameter
，
In order to wet the circumference of the fabric,
in order to release heat for the chemical reaction,
the density is expressed as a function of time,
the speed is indicated in the form of a speed,
internal energy is shown, and A is the area.
As a preferred technical solution, the quasi-one-dimensional control equation is solved by using a MacCormack finite difference method.
As an optimized technical scheme, the pre-estimation step adopts forward difference to calculate the spatial derivative, the correction step adopts backward difference to calculate the spatial derivative, and the finally obtained numerical result achieves second-order precision in time and space.
As a preferred technical solution, the sixth step further includes:
assigning a nozzle inlet parameter to an interface between the ramjet and the ramjet channel;
and calculating the flow field characteristic of the stamping channel spray pipe according to the calculation result of the stamping engine so as to obtain the flow characteristic of the spray pipe.
Compared with the prior art, the invention has the beneficial effects that: the method is used for carrying out the numerical simulation of the hypersonic flight vehicle and the internal and external flows of the propulsion system, so that the internal and external flow characteristics of the hypersonic flight vehicle can be obtained with certain numerical simulation precision, the pre-research period can be shortened, and the updating iteration of the design scheme is accelerated.
Drawings
FIG. 1 is a diagram of a hypersonic aircraft and its combined power propulsion system model provided in accordance with an embodiment of the present invention;
FIG. 2 is a compressor map provided in accordance with an embodiment of the present invention;
FIG. 3 is a turbine map provided in accordance with an embodiment of the present invention;
in the figure, 1-aircraft body, 2-turbine channel, 3-inlet and turbine engine interface, 4-turbine engine, 5-turbine engine and nozzle interface, 6-turbine channel nozzle, 7-ramjet channel nozzle, 8-ramjet combustion chamber and ramjet channel nozzle interface, 9-bimodal ramjet combustion chamber, 10-inlet and ramjet engine interface, 11-ramjet channel, 12-precursor shock.
Detailed Description
The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
Referring to fig. 1, the present embodiment provides a simulation method for a combined power system, including the steps of:
step one, acquiring air flow parameters entering a turbine channel 2 and a stamping channel 11;
specifically, after being compressed by the precursor shock wave 12, the gas flow enters the turbine channel 2 and the ram channel 11 of the inlet channel, respectively, and the gas flow parameters at these two locations are obtained, in this embodiment, the gas flow parameters include: flow rate, static pressure, mach number, etc.;
secondly, converting the gas flow parameters of the turbine channel 2 and the stamping channel 11 into first one-dimensional data and second one-dimensional data at an interface through area averaging or mass averaging respectively;
specifically, the air flow parameters entering the turbine passage 2 are averaged by area or mass at the interface 3 of the inlet and the turbine engine; the air flow parameters entering the ramjet channel 11 are averaged by area or mass at the inlet to ramjet interface 10;
inputting the first one-dimensional data into the turbine engine 4, and determining inlet parameters of a turbine channel spray pipe 6 by the turbine engine 4 by adopting a component characteristic model;
specifically, after the first one-dimensional data is input to the turbine engine 4, the turbine engine 4 performs calculations using a component characteristics model, wherein compressor and turbine characteristics are shown in fig. 2 and 3, respectively.
In this embodiment, the turbine engine model includes an air intake duct, an air compressor, a main combustion chamber, a turbine, an afterburner, and a nozzle, and the input parameters include a flight height, a mach number, and a throttle lever angle. In order to smoothly perform the thermodynamic cycle calculation, in the present embodiment, the turbine engine 4 selects initial values of three parameters in total, which are the compressor rotation speed, the compressor auxiliary coordinate, and the turbine pressure drop ratio. According to the concept of engine component common operation, the single-shaft turbojet engine must satisfy the following three common operating conditions:
(1) the flow of the outlet of the compressor and the flow of the inlet of the turbine are continuous;
(2) the compressor and the turbine work are balanced;
(3) flow of the spray pipe is balanced;
iteratively updating the initial values of the three parameters by adopting a Newton-Raphson method according to a common working condition equation, and when the error is less than 10-4And stopping iteration, acquiring a nozzle inlet parameter after convergence, and assigning the parameter to an inlet boundary condition in numerical simulation.
Fourthly, the turbine channel spray pipe performs flow field characteristic calculation by utilizing the inlet parameters of the turbine channel spray pipe, so that the flow characteristic of the turbine channel spray pipe is obtained;
specifically, after the calculation of the turbine engine 4 is completed, the nozzle inlet parameter is assigned to the turbine engine and nozzle interface 5, the turbine channel nozzle 6 performs flow field characteristic calculation according to the calculation result of the turbine engine 4, and the flow characteristic of the turbine channel nozzle 6 is obtained.
Inputting the second one-dimensional parameters into a ramjet engine, and determining inlet parameters of a spray pipe of a stamping channel by the ramjet engine through a quasi one-dimensional mathematical model;
specifically, the other air flow compressed by the aircraft body 1 enters a stamping channel 11, is further compressed by a shock wave string, enters a double-module stamping combustion chamber 9 through an air inlet channel and a stamping engine interface 10, the double-module stamping combustion chamber 9 is analyzed by adopting a quasi one-dimensional mathematical model, and stroke parameters of the stamping engine are obtained by solving a conservation type quasi one-dimensional control equation (1). The source items of the control equation consider factors such as mass addition, area change, wall friction, chemical reaction heat release and the like, and the control equation is as follows:
wherein
In order to solve the vector, the vector is calculated,
in the form of a flux vector, the flux vector,
the definition for the source term is as follows:
wherein,
adding terms for mass;
is the wall friction coefficient; equivalent diameter
，
In order to wet the circumference of the fabric,
in order to release heat for the chemical reaction,
the density is expressed as a function of time,
the speed is indicated in the form of a speed,
the internal energy and the area are shown as A.
In this embodiment, the maccormac finite difference method, which is a time-marching estimation-correction algorithm, is used to solve the control equation. The spatial derivative is calculated by adopting forward difference in the pre-estimation step, the spatial derivative is calculated by adopting backward difference in the correction step, and the finally obtained numerical result reaches second-order precision in time and space.
And sixthly, calculating the flow field characteristic of the stamping channel spray pipe according to the inlet parameter of the stamping channel spray pipe, and obtaining the flow characteristic of the stamping channel spray pipe.
Specifically, after the calculation of the dual-mode ramjet combustor 9 is completed, the parameters of the inlet of the nozzle are assigned to the interface 8 of the ramjet combustor and the ramjet channel, and the ramjet channel 7 performs flow field characteristic calculation according to the calculation result of the ramjet engine, so as to obtain the flow characteristics of the ramjet channel 7.
The simulation method is used for carrying out the numerical simulation of the hypersonic flight vehicle and the propulsion system integrating the internal flow and the external flow, can ensure certain numerical simulation precision to obtain the internal flow and the external flow characteristics of the hypersonic flight vehicle, can shorten the pre-research period, and can accelerate the updating iteration of the design scheme.
In addition, the embodiment of the present invention further provides a computer readable storage medium, wherein the computer readable storage medium may store a program, and the program comprises part or all of the steps of any one of the simulation methods for a combined power system described in the above method embodiments when executed.
In addition, functional units in the embodiments of the present invention may be integrated into one processing unit, or each unit may exist alone physically, or two or more units are integrated into one unit. The integrated unit may be implemented in the form of hardware, or may also be implemented in the form of a software functional unit.
The integrated unit, if implemented in the form of a software functional unit and sold or used as a stand-alone product, may be stored in a computer readable memory. Based on such understanding, the technical solution of the present invention may be embodied in the form of a software product, which is stored in a memory and includes several instructions for causing a computer device (which may be a personal computer, a server, a network device, or the like) to execute all or part of the steps of the method according to the embodiments of the present invention. And the aforementioned memory comprises: a U-disk, a Read-Only Memory (ROM), a Random Access Memory (RAM), a removable hard disk, a magnetic or optical disk, and other various media capable of storing program codes.
Those skilled in the art will appreciate that all or part of the steps in the methods of the above embodiments may be implemented by associated hardware instructed by a program, which may be stored in a computer-readable memory, which may include: flash Memory disks, Read-Only memories (ROMs), Random Access Memories (RAMs), magnetic or optical disks, and the like.
An exemplary flow chart of a simulation method for a combined power system according to an embodiment of the present invention is described above with reference to the drawings. It should be noted that the numerous details included in the above description are merely exemplary of the invention and are not limiting of the invention. In other embodiments of the invention, the method may have more, fewer, or different steps, and the order, inclusion, function, etc. of the steps may be different from that described and illustrated.
Claims (10)
1. A simulation method for a combined power system, comprising:
step one, acquiring air flow parameters entering a turbine channel and a stamping channel;
secondly, converting the gas flow parameters of the turbine channel and the stamping channel into first one-dimensional data and second one-dimensional data at an interface through area averaging or mass averaging respectively;
inputting the first one-dimensional data into a turbine engine, and determining the inlet parameters of a turbine channel spray pipe by the turbine engine by adopting a component characteristic model;
fourthly, the turbine channel spray pipe performs flow field characteristic calculation by utilizing the inlet parameters of the turbine channel spray pipe, so that the flow characteristic of the turbine channel spray pipe is obtained;
inputting the second one-dimensional parameters into a ramjet engine, and determining inlet parameters of a spray pipe of a stamping channel by the ramjet engine through a quasi one-dimensional mathematical model;
and sixthly, calculating the flow field characteristic of the stamping channel spray pipe according to the inlet parameter of the stamping channel spray pipe, and obtaining the flow characteristic of the stamping channel spray pipe.
2. The simulation method according to claim 1, wherein the second step further comprises:
and multiplying the airflow parameter in each grid unit by the area or flow of the grid unit, then summing the parameters of the whole interface, and finally dividing by the area or flow of the interface to obtain the area average or quality average parameter.
3. The simulation method according to claim 1, wherein the step three further comprises:
determining an initial value of a preset parameter of the turbine engine from the first one-dimensional data;
performing iterative updating according to a common working condition equation and by adopting a Newton-Raphson method for the initial values of the preset parameters, and when the error is less than 10-4And when so, stopping iteration.
4. The simulation method according to claim 3, wherein: the preset parameters comprise the rotating speed of the gas compressor, the auxiliary coordinate of the gas compressor and the pressure drop ratio of the turbine.
5. The simulation method according to claim 1, wherein the fourth step further comprises:
assigning a nozzle inlet parameter to an interface between the turbine engine and the turbine path nozzle;
and the turbine channel spray pipe performs flow field characteristic calculation according to the calculation result of the turbine engine so as to obtain the flow characteristic of the turbine channel spray pipe.
6. The simulation method according to claim 1, wherein the step five further comprises:
a double-module stamping combustion chamber of the stamping engine adopts a quasi-one-dimensional mathematical model for analysis;
calculating to obtain stroke parameters of the ramjet by solving a conservation quasi-one-dimensional control equation;
wherein
In order to solve the vector, the vector is calculated,
in the form of a flux vector, the flux vector,
the definition for the source term is as follows:
wherein,
adding terms for mass;
is the wall friction coefficient; equivalent diameter
，
In order to wet the circumference of the fabric,
in order to release heat for the chemical reaction,
the density is expressed as a function of time,
the speed is indicated in the form of a speed,
internal energy is shown, and A is the area.
7. The simulation method according to claim 6, wherein: and solving the quasi-one-dimensional control equation by adopting a MacCormack finite difference method.
8. The simulation method according to claim 7, wherein: the pre-estimation step adopts forward difference to calculate the spatial derivative, the correction step adopts backward difference to calculate the spatial derivative, and the finally obtained numerical result reaches second-order precision in time and space.
9. The simulation method according to claim 1, wherein the sixth step further comprises:
assigning a nozzle inlet parameter to an interface between the ramjet and the ramjet channel;
and calculating the flow field characteristic of the stamping channel spray pipe according to the calculation result of the stamping engine so as to obtain the flow characteristic of the spray pipe.
10. A computer-readable storage medium, in which a computer program is stored which, when being executed by a processor, carries out the steps of a simulation method for a combined power system according to any one of claims 1 to 9.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210331010.8A CN114626146B (en) | 2022-03-31 | 2022-03-31 | Simulation method for combined power system |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210331010.8A CN114626146B (en) | 2022-03-31 | 2022-03-31 | Simulation method for combined power system |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN114626146A true CN114626146A (en) | 2022-06-14 |
| CN114626146B CN114626146B (en) | 2024-08-09 |
Family
ID=81903266
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202210331010.8A Active CN114626146B (en) | 2022-03-31 | 2022-03-31 | Simulation method for combined power system |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN114626146B (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN117382889A (en) * | 2023-12-12 | 2024-01-12 | 中国航空工业集团公司金城南京机电液压工程研究中心 | Power system of high-speed aircraft and transition stage mode switching method thereof |
Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105539862A (en) * | 2016-01-14 | 2016-05-04 | 南京航空航天大学 | Series-connection type hybrid power air intake duct translation type modal conversion device |
| WO2017084106A1 (en) * | 2015-11-20 | 2017-05-26 | 田川 | System and method for numerical simulation of aircraft flow field |
-
2022
- 2022-03-31 CN CN202210331010.8A patent/CN114626146B/en active Active
Patent Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2017084106A1 (en) * | 2015-11-20 | 2017-05-26 | 田川 | System and method for numerical simulation of aircraft flow field |
| CN105539862A (en) * | 2016-01-14 | 2016-05-04 | 南京航空航天大学 | Series-connection type hybrid power air intake duct translation type modal conversion device |
Non-Patent Citations (2)
| Title |
|---|
| ABDULMAJEED A. RAMADHAN 等: "Numerical modelling of electrohydrodynamic airflow indecud in a wire-to-grid channel", JOURNAL OF ELECTROSTATICS, vol. 87, 30 June 2017 (2017-06-30), pages 123 - 139, XP085116979, DOI: 10.1016/j.elstat.2017.04.004 * |
| 牛彦沣 等: "并联TBCC排气系统流场结构数值模拟及实验研究", 推进技术, vol. 38, no. 12, 23 October 2017 (2017-10-23), pages 2686 - 2691 * |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN117382889A (en) * | 2023-12-12 | 2024-01-12 | 中国航空工业集团公司金城南京机电液压工程研究中心 | Power system of high-speed aircraft and transition stage mode switching method thereof |
| CN117382889B (en) * | 2023-12-12 | 2024-02-09 | 中国航空工业集团公司金城南京机电液压工程研究中心 | Power system of high-speed aircraft and transition stage mode switching method thereof |
Also Published As
| Publication number | Publication date |
|---|---|
| CN114626146B (en) | 2024-08-09 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| Novak | Streamline curvature computing procedures for fluid-flow problems | |
| CN107885891B (en) | Method for optimizing overall performance of aircraft engine | |
| CN109408934B (en) | Turbine engine whole machine quasi-three-dimensional flow virtual numerical test method | |
| CN113361211B (en) | Method, system, equipment and medium for calculating aerodynamic stability of turboshaft engine | |
| Zhewen et al. | A multi-fidelity simulation method research on front variable area bypass injector of an adaptive cycle engine | |
| Liu et al. | On the mode transition of a double bypass variable cycle compression system | |
| Vieweg et al. | Collaborative aircraft engine preliminary design using a virtual engine platform, part B: application | |
| Yang et al. | Full-engine simulation of micro gas turbine based on time-marching throughflow method | |
| CN114626146A (en) | Simulation method for combined power system | |
| Xu et al. | Effect of rotor axial blade loading distribution on compressor stability | |
| CN117993261A (en) | Simulation calculation method for whole engine surge dynamic process of aero-engine | |
| Xu et al. | An efficient multi-fidelity simulation method for adaptive cycle engine ejector nozzle performance evaluation | |
| Ismail et al. | Simulation of aircraft gas turbine engines | |
| Jia et al. | Research on the volume-based fully coupled method of the multi-fidelity engine simulation | |
| Xi et al. | Design of thrust augmentation control schedule during mode transition for turbo-ramjet engine | |
| CN111523201B (en) | Internal and external flow field coupling iterative calculation method under engine reverse thrust state | |
| Zhang et al. | An integrated modeling approach for variable cycle engine performance analysis | |
| CN116127815B (en) | Modeling method of turbofan engine with injection nozzle | |
| CN116151157A (en) | Calculation method for simulating surge hammering wave load of engine | |
| Kim | Application of machine learning and its effectiveness in performance model adaptation for a turbofan engine | |
| Powers et al. | Unsteady simulation of a single stage high speed compressor with advanced casing treatments | |
| Righi et al. | Three-dimensional low-order surge model for high-speed axial compressors | |
| Moroz et al. | Integrated environment for gas turbine preliminary design | |
| Stewart | Axisymmetric aerodynamic numerical analysis of a turbofan engine | |
| Zhang et al. | Optimization of cycle parameters of variable cycle engine based on response surface model |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |